Split ring seal with spring element

ABSTRACT

A split ring seal assembly includes a metal seal ring having two ends defining a circumferential gap therebetween. At least a first spring element is mounted to the two ends to bias the two ends circumferentially towards each other to reduce the diameter of a circumferential inner sealing surface of the metal seal ring.

TECHNICAL FIELD

The described concept relates generally to gas turbine engines, and moreparticularly, to seals used therein.

BACKGROUND OF THE ART

Gas turbine engines are formed of stator components which are suitablyjoined together to define working fluid paths for directing for example,compressed air, hot combustion gases, etc. therethrough. Various typesof static seals must be provided between the stator components to reduceor prevent undesirable leakage of either the pressurized air or the hotcombustion gases. Some seals are full rings, or may be circumferentiallysplit at one location to eliminate undesirable hoop stress therein. Theseals are subject to various differential thermal movement between theadjoining components, including differential radial and/or axialmovement. Relative radial and axial deflections are common between theaft end of the combustor outer liner and the forward end of the outerband of the adjoining high pressure turbine nozzle. Under the hightemperature of the combustion gases produced in the combustor, the outerliner can expand radially outwardly, significantly more than theradially outer expansion of the outer end of the adjoining high pressureturbine nozzle. Furthermore, the axial gap between the two componentsmay also grow substantially larger during operation.

Accordingly, there is a need to provide an improved sealing ring forsealing high excursion differential radial and axial movement betweengas turbine engine stator components.

SUMMARY OF THE INVENTION

In one aspect, there is provided a split ring seal assembly for a gasturbine engine comprising: a seal ring made of a metal material havingfirst and second ends defining a circumferential gap between the twoends, the seal ring defining a circumferential inner sealing surfaceextending axially between opposed first and second axial sides of theseal ring; and a first spring element mounted to the respective firstand second ends of the seal ring and biasing the two endscircumferentially towards each other, for radially compressing the sealrings and thereby reducing the diameter of the circumferential innersealing surface.

In another aspect, there is provided a split ring seal assembly for agas turbine engine comprising: a seal ring made of a metal materialhaving first and second ends defining a circumferential gap between thetwo ends, the seal ring defining a circumferential inner sealing surfaceextending axially between opposed first and second axial sides of theseal ring, for radially contacting a circumferential outer surface of afirst stator component of the engine, the seal ring further defining aradial end sealing surface on the first axial side of the seal ring foraxially contacting a radial end surface of a second stator component ofthe engine; means for biasing the first and second ends of the seal ringcircumferentially towards each other, thereby reducing the diameter ofthe circumferential inner sealing surface to radially compress thecircumferential inner sealing surface onto the circumferential outersurface of the first stator component of the engine; and means forbiasing the seal ring axially towards the second stator component of theengine to press the radial end sealing surface against the radial endsurface of the second stator component of the engine, thereby sealing anaxial gap between the first and second of the stator components of theengine.

Further details of these and other aspects of the present describedconcept will be apparent from the detailed description and drawingsincluded below.

DESCRIPTION OF THE DRAWINGS

Reference is now made to the accompanying drawings depicting aspects ofthe described concept, in which:

FIG. 1 is a schematic cross-sectional view of a turbofan gas turbineengine as an application of the described concept;

FIG. 2 is a partial schematic cross-sectional view of the gas turbineengine in FIG. 1, showing the circled area indicated by numeral 2 inwhich a split ring seal assembly is employed according to oneembodiment;

FIG. 3 is a perspective view of a seal ring used in the split ring sealassembly of FIG. 2;

FIG. 4 is a partial perspective view of the seal ring of FIG. 3, showingtwo ends of the seal ring with a first spring element mounted thereon;

FIG. 5 is a partial perspective view of the split ring seal assembly ofFIG. 2, showing the seal ring positioned around a gas exit end of acombustor with first and second spring elements attached thereto toapply circumferential and axial spring forces to the seal ring,respectively; and

FIG. 6 is a view of a split ring seal assembly similar to FIG. 2,according to a further embodiment.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring to FIG. 1, a turbofan gas turbine engine presented as anexample of the application of the described concept, includes a housing10, a core casing 13, a low pressure spool assembly seen generally at 12which includes a fan assembly 14, a low pressure compressor assembly 16,a low pressure turbine assembly 18, and a high pressure spool assemblyseen generally at 20 which includes a high pressure compressor assembly22 and a high pressure turbine assembly 24. The core casing 13 surroundsthe low and high pressure spool assemblies 12 and 20 in order to definea main fluid path (not numbered) therethrough. In the main fluid paththere is provided a combustor 28 to constitute a gas generator section26.

Referring to FIGS. 1-5 a vane stator shroud 32 of the high pressureturbine assembly 24 is positioned downstream of a gas exit end 30 of thecombustor 28, as more clearly shown in FIG. 2. The combustor 28 and thevane stator shroud 32 are provided with a plurality of radiallyextending support elements 34, 36, respectively which are engaged with astationary support structure 38 of the engine to retain the combustor 28and the vane stator shroud 32 in axial positions adjacent to each other.Therefore, combustion gases produced in the combustor 28 are dischargedfrom the gas exit end 30, to flow into the vane stator shroud 32 inorder to power the turbine (not numbered) of the high pressure turbineassembly 24. A split ring seal assembly 40 according to one embodiment,is seated on a circumferential outer surface 42 of the gas exit end 30of the combustor 28, to abut a radial end surface 44 defined on aforward end of the vane stator shroud 32, thereby sealing an axialclearance 46 between the gas exit end 30 of the combustor 28 and thevane stator shroud 32 of the high pressure turbine assembly 24.

The split ring seal assembly 40 according to this embodiment, includes aseal ring 48 made of metal material (see FIGS. 3-5). The metal seal ring48 is a type of split ring and has two ends 50, 52 defining thecircumferential gap 54 therebetween. The metal seal ring 48 defines acircumferential inner sealing surface 56 along the inner circumferentialside thereof, extending axially between opposed axial sides 58, 60 ofthe metal seal ring 48. The circumferential inner sealing surface 56 ofthe metal seal ring 48 is adapted to radially contact thecircumferential outer surface 42 of the gas exit end 30 of the combustor28. The metal seal ring 48 further defines a radial end sealing surface61 on one of the two axial sides, such as axial side 60, for axiallycontacting the radial end surface 44 of the vane stator shroud 32.

The split ring seal assembly 40 includes means for biasing the ends 50,52 of the metal seal ring 48 circumferentially towards each other, inorder to reduce the diameter of the circumferential inner sealingsurface 56 and to radially compress the circumferential inner sealingsurface 56 onto the circumferential outer surface 42 of the gas exit end30 of the combustor 28, thereby assuring a firm radial contact betweenthe two components to avoid formation of gas passages therebetween. Forexample, the means may comprise a torsion spring 62 mounted to therespective ends 50, 52 of the metal seal ring 48. For convenience ofmounting the torsion spring 62, the two ends 50, 52 of the metal sealring 48 may be provided with respective integral lands 64, 66 radiallyoutwardly projecting from ends 50, 52, which define mounting holes (notnumbered), for example, axially extending through the lands to engagetwo free ends (not numbered) of torsion spring 62. The torsion spring 62may be pre-tensioned by forcing the two ends thereof away from eachother to align with the mounting holes in the respective lands 64, 66when the torsion spring 62 is mounted to the split ring assembly 40.Therefore, the pre-tensioned torsion spring 62 biases the two ends 50,52 of the metal seal ring 48 circumferentially towards each other.

The split ring seal assembly 40 is also provided with, in accordancewith this embodiment, means for biasing the metal seal ring 48 axiallytowards the vane stator shroud 32, in order to press the radial endsealing surface 61 against the radial end surface 44 of the vane statorshroud 32. For example the means may comprise an annular wave springring 68 which has a spring-shaped axial cross section as shown in FIG.2. The annular wave spring ring 68 is positioned around the gas exit end30 of the combustor 28 and is axially located between a flange 69 whichextends radially and outwardly from the gas exit end 30 of the combustor28, and the axial side 58 of the metal seal ring 48, in a pre-axiallypressed condition. Therefore, the annular wave spring ring 68 abuts theflange 69 of the combustor 28 and biases the metal seal ring. 48 towardsand against the radial end surface 44 of the vane stator shroud 32.Under the axial spring force of the annular wave spring ring 68, theradial end sealing surface 61 of the metal seal ring 48 firmly axiallycontacts the radial end surface 44 of vane stator shroud 32 to therebyavoid formation of gas passages therebetween.

Due to the radial sealing between the circumferential inner sealingsurface 56 of the metal seal ring 48 and the circumferential outersurface 42 of the gas exit end 30 of the combustor 28, and also due tothe axial sealing between the radial end sealing surface 61 of the metalseal ring 48 and the radial end surface 44 of the vane stator shroud 32,the axial clearance 46 between the gas exit end 30 of the combustor 28and the forward end of the vane stator shroud 32 is therefore sealed.

The torsion spring 62, which may be located at the axial side 58 of themetal seal ring 48 as is the annular wave spring 68, may bealternatively replaced by a spring element of any type which applies apair of spring forces to the respective ends 50, 52 of the metal sealring 48 in order to bias the respective ends 50, 52 circumferentiallytowards each other, such as coil springs, leaf springs, spring clips,etc. The annular wave spring ring 68 may be replace alternatively by aspring ring of another type such as having a U-shaped or V-shaped axialcross section, or may be alternatively replaced by a plurality of springelements which may be axially pressed to bias the metal spring ring 48axially towards the vane stator shroud 32. For example, three or foursuch axial pressing spring elements may be positioned circumferentiallyequally spaced apart one from another. Positioning and retaining meansmay be provided with either the gas exit end 30 of the combustor 28 orwith the metal seal ring 48 for maintaining the circumferential evenlyspaced positions of the individual axial pressing spring elements.

It should be noted that due to the radial and circumferential thermalexpansion of the gas exit end 30 of the combustor 28 during engineoperation, the two ends 50 and 52 of the metal seal ring 48 may beforced away from each other such that the circumferential gap 54 betweenthe two ends 50 and 52 increases. Therefore, it is optional according toanother embodiment to provide an overlap joint 70 to close thecircumferential gap 54.

The overlap joint 70 which is like a flat tongue member having arelatively thin thickness with respect to the radial thickness of themetal seal ring 48, may be integrated with and extend from the end 52 atthe inner circumferential side of the metal seal ring 48,circumferentially over the gap 54. The metal seal ring 48 furtherdefines a radial recess 72 on the inner circumferential side of themetal seal ring 48 at the end 50. The overlap joint 70 extendscircumferentially from the end 52 , into the radial recess 72. Theradial recess 72 has a radial dimension substantially equal to thethickness of the overlap joint 70 such that the inner surface of theoverlap joint 70 is located in a radial position substantiallydetermined by the diameter of the circumferential inner sealing surface56 of the metal seal ring 48, thereby forming part of thecircumferential inner sealing surface 56 of the metal seal ring 48. Aside surface (not numbered) of the overlap joint 70 also forms part ofthe radial end sealing surface 61 on the axial side 60 of the metal sealring 48. Therefore, in a working condition the overlap joint 70 as partof the metal seal ring 48, also firmly radially contacts thecircumferential outer surface 42 of the gas exit end 30 of the combustor28 and firmly axially contacts the radial end surface 44 of the vanestator shroud 32.

The radial recess 72 may have a circumferential dimension greater than acircumferential dimension of the overlap joint 70, in order to define agap (not numbered) between a free end (not numbered) of the overlapjoint 70 and an end wall (not numbered) of the radial recess 72. As aresult, the gap between the free end of the overlap joint 70 and the endwall of the radial recess 72 is greater than the circumferential gap 54between the two ends 50 and 52 of the metal seal ring 48 to therebyavoid interference with a relative motion between the two ends 50 and 52under the spring forces of the torsion spring 62 when thermal expansionof the gas exit end 30 of the combustor 28 changes.

The torsion spring 62 and the annular wave spring ring 68 providerespective circumferential and axial loads to the metal seal ring 48 andkeep the seal ring in firm radial and axial contact with the respectivecombustor 28 and the vane stator shroud 32, and furthermore, providesome degree of flexibility of the metal seal ring 48 for the thermalgrowth at any running condition of the engine, without incurring “creep”issues due to the rigid connections of conventional split ring sealassemblies. The overlap joint 70 is used to minimize gas leakagesthrough the split area of the metal seal ring 48.

The metal seal ring 48 contacts the combustor 28 and the vane statorshroud 32 in different directions (radial and axial). Therefore,different radial thermal expansions of the combustor 28 and the vanestator shroud 32 do not affect the sealing result provided by the metalseal ring 48. Nevertheless, the metal seal ring 48 may be used in othersealing arrangements.

FIG. 6 illustrates another application of the split ring seal assembly40 according to a further embodiment. Components and features shown inFIG. 6 which are similar to those shown in FIGS. 1-5, are indicated bysimilar reference numerals, and will not be redundantly described. Themetal seal ring 48 according to this embodiment, has an axial dimensionfor radially contacting both the circumferential outer surface 42 of thegas exit end 30 of the combustor 28 and a circumferential outer surface43 of the vane stator shroud 32, to thereby seal an axial clearance 46between the gas exit end 30 of the combustor 28 and the vane statorshroud 32. In particular, the circumferential outer surface 43 isdefined on an axial flange 41 extending forwardly from the forward endof the vane stator shroud 32, and has a diameter substantially equal tothe diameter of the circumferential outer surface 42 of the gas exit end30 of the combustor 28. The axial clearance 46 is located axiallybetween the gas exit end 30 of the combustor 28 and the axial flange 41of the vane stator shroud 32 when the vane stator shroud 32 ispositioned downstream of and adjacent to the combustor 28. The metalseal ring 48 is axially positioned and restrained between the radialflange 69 of the combustor 28 and the radial end surface 44 of the vanestator shroud 32. Therefore, the annular wave spring ring 68 shown inFIG. 2 or the like is not needed because only radial compressions arerequired for radially contacting both the circumferential outer surfaces42 and 43 of the respective combustor 28 and the vane stator shroud 32.

The above description is meant to be exemplary only and one skilled inthe art would recognize that changes may be made to the embodimentsdescribed without departure from the described concept. For example, thesplit ring seal assembly is described to seal the axial clearancebetween a combustor and a vane stator shroud of a high pressure turbineassembly according to the described embodiments, however, the split ringseal assembly may be used for sealing axial gaps between two annular gasturbine engine components of all types, such as annular components usedin fan assembly, high or low pressure compressor assemblies and in highor low pressure turbine assemblies of gas turbine engines. The splitring seal assembly may be used in gas turbine engines of any typealthough a turbofan gas turbine engine is used as an exemplaryapplication of the split ring seal assembly. Other modifications whichfall within the scope of the described concept will be apparent to thoseskilled in the art, in light of a review of this disclosure and suchmodifications are intended to fall within the appended claims.

1. A split ring seal assembly for a gas turbine engine comprising: a seal ring made of a metal material having first and second ends defining a circumferential gap between the two ends, the seal ring defining a circumferential inner sealing surface extending axially between opposed first and second axial sides of the seal ring; and a first spring element mounted to the respective first and second ends of the seal ring and biasing the two ends circumferentially towards each other, for radially compressing the seal ring and thereby reducing the diameter of the circumferential inner sealing surface.
 2. The split ring seal assembly as defined in claim 1 wherein the circumferential inner sealing surface of the seal ring is adapted to contact a circumferential outer surface of a first stator component of the engine, and wherein the seal ring further defines a radial end sealing surface on the first axial side of the seal ring for axially contacting a radial end surface of a second stator component of the engine to thereby seal an axial gap between the first and second stator components of the engine.
 3. The split ring seal assembly as defined in claim 2 further comprising a second spring element biasing the seal ring axially towards the second stator component of the engine.
 4. The split ring seal assembly as defined in claim 3 wherein the first and second spring elements are positioned at the second axial side of the seal ring.
 5. The split ring seal assembly as defined in claim 1 wherein the first spring element comprises a torsion spring having two ends releaseably engaged with the respective two ends of the seal ring.
 6. The split ring seal assembly as defined in claim 1 wherein the seal ring comprises an overlap joint integrated with the first end of the seal ring and extending circumferentially over the gap between the two ends of the seal ring.
 7. The split ring seal assembly as defined in claim 6 wherein the seal ring defines a radial recess on a radial inner side of the second end of the seal ring for receiving the overlap joint extending from the first end of the seal ring, the overlap joint forming part of the circumferential inner sealing surface.
 8. The split ring seal assembly as defined in claim 7 wherein the first and second ends of the seal ring each comprise a land projecting radially outwardly from the respective first and second end, each of the lands defining a mounting hole for engagement with the first spring element.
 9. The split ring seal assembly as defined in claim 8 wherein the land radially outwardly projecting from the second end has a circumferential dimension greater than a circumferential dimension of the radial recess.
 10. The split ring seal assembly as defined in claim 1 wherein the circumferential inner sealing surface of the seal ring has an axial dimension for radially contacting the circumferential outer surface of the first stator component and a circumferential outer surface of a second stator component of the engine to thereby seal an axial gap between the first and second stator components.
 11. A split ring seal assembly for a gas turbine engine comprising: a seal ring made of a metal material having first and second ends defining a circumferential gap between the two ends, the seal ring defining a circumferential inner sealing surface extending axially between opposed first and second axial sides of the seal ring, for radially contacting a circumferential outer surface of a first stator component of the engine, the seal ring further defining a radial end sealing surface on the first axial side of the seal ring for axially contacting a radial end surface of a second stator component of the engine; means for biasing the first and second ends of the seal ring circumferentially towards each other, thereby reducing the diameter of the circumferential inner sealing surface, to radially compress the circumferential inner sealing surface onto the circumferential outer surface of the first stator component of the engine; and means for biasing the seal ring axially towards the second stator component of the engine to press the radial end sealing surface against the radial end surface of the second stator component of the engine, thereby sealing an axial gap between the first and second of the stator components of the engine.
 12. The split ring seal assembly as defined in claim 11 wherein the seal ring comprises an overlap joint integrated with the first end of the seal ring and extending circumferentially over the gap between the two ends of the seal ring.
 13. The split ring seal assembly as defined in claim 12 wherein the seal ring defines a radial recess on an inner peripheral side of the seal ring at the second end, the overlap joint extending from the first end of the seal ring into the radial recess, an inner surface of the overlap joint forming part of the circumferential inner sealing surface of the seal ring and a side surface of the overlap joint forming part of the radial end sealing surface on the first axial side of the seal ring.
 14. The split ring seal assembly as defined in claim 1.3 wherein the seal ring defines a gap between a free end of the overlap joint and an end wall of the radial recess, the gap between the free end of the overlap joint and the end wall of the radial recess being greater than the gap between the first and second ends of the seal ring.
 15. The split ring seal assembly as defined in claim 14 wherein the first and second ends of the seal ring each comprise a land radially outwardly projecting from the respective first and second end, the land radially outwardly projecting from the second end has a circumferential dimension greater than the circumferential dimension of the radial recess.
 16. The split ring seal assembly as defined in claim 11 wherein the means for biasing the first and second ends of the seal ring circumferentially towards each other comprises a spring element having two ends mounted to the respective first and second ends of the seal ring.
 17. The split ring seal assembly as defined in claim 11 wherein the means for biasing the seal ring axially towards the second stator component of the engine comprises at least one spring element positioned between a radial wall of the first stator component of the engine and the second side of the seal ring. 